Abstract: A blade wheel of a turbomachine, which blade wheel has a multiplicity of blades which are suitable and provided for extending radially in a flow path of the turbomachine, wherein the blades form a blade entry angle and a blade exit angle. Provision is made whereby the blade wheel forms N blocks of blades, where N?2, wherein the blades of a block have in each case the same blade entry angle and the same blade exit angle, and the blades of at least two mutually adjacent blocks have a different blade entry angle and/or a different blade exit angle. According to a further aspect of the invention, partial gaps that the blades form in relation to an adjacent flow path boundary are varied in mutually adjacent blocks.

Abstract: An air moving device according to the present disclosure can include a housing and an installation hub. The housing can be connected to the installation hub via one or more adjustable supports. An impeller can be installed at least partially in the housing and configured to direct air out of the housing. In some embodiments, the adjustable supports can be adjusted to move the housing with respect to the installation hub. For example, the adjustable supports can be configured to modify the tilt of the housing and/or the overall distance between the housing and the installation hub. The installation hub can be installed on a ceiling, wall, or other mounting surface. Adjustment of the adjustable supports can permit vertical alignment of the air moving device housing, even when the installation hub is mounted to a slanted or sloped (e.g., non-horizontal) ceiling or wall.

Abstract: A system and modular compressor for raising the pressure in production gas is disclosed, wherein in a set of compressor modules each second module is a rotor module carrying an impeller driven in rotation relative to an adjacent stationary module, a rotor module and a stationary module in combination providing a compressor stage in which production gas is accelerated through a flow duct that passes an interface between the rotor module and the stationary module, wherein at the interface at least one bearing for axial and/or radial load is provided for journaling the rotor module on the stationary module. The at least one bearing is a gas bearing, wherein a passage is arranged in the stationary module to lead an extracted portion of production gas at raised pressure from the compressor to the gas bearing(s).

Abstract: A gas turbine engine component includes a vane arc segment that defines an axis. The vane arc segment includes an airfoil section and first and second platforms. The airfoil section has a first radial end, a second radial end, a first side, a second side, a leading edge, and a trailing edge. The airfoil section has associated characteristics, including a center of pressure and an aerodynamic load vector through the center of pressure. The first platform defines a first side chevron face that has a leading leg and a trailing leg that meet at an angle. The leading leg is elongated along a centerline that is non-axially oriented with respect to the axis, the leading leg meets the leading face at a leading first side corner. The leading first side corner is located outside of the aerodynamic load vector relative to the leading edge of the airfoil section.

Abstract: A variable guide vane (VGV) apparatus has a variable guide vane (VGV) rotatable about a vane rotation axis. An actuating arm is mounted to the VGV. The actuating arm has a fork defining a slot for receiving a drive pin. The slot is profiled to accommodate angular misalignment between the pin and the fork throughout a range of motion of the associated pin along the slot.

Abstract: A variable guide vane (VGV) apparatus has a variable guide vane (VGV) rotatable about a vane rotation axis. An actuating arm is mounted to the VGV. The actuating arm has a fork defining a slot for receiving a drive pin. The slot has a curved contour configured to act as a vane angle schedule adjustment.

Abstract: A variable geometry turbocharger includes: a turbine rotor; and a variable nozzle mechanism for adjusting a flow of exhaust gas to the turbine rotor from a scroll flow passage formed on a radially outer side of the turbine rotor. The variable nozzle mechanism includes: a nozzle vane disposed in an exhaust gas flow passage for guiding the exhaust gas to the turbine rotor from the scroll flow passage; a support wall forming a flow passage wall on a first side of the exhaust gas flow passage with respect to an axial direction of the turbine rotor and supporting the nozzle vane rotatably in a cantilever fashion; and a non-support wall forming a flow passage wall on a second side of the exhaust gas flow passage with respect to the axial direction. Of an end surface of the nozzle vane on a side of the non-support wall, an edge portion on a side of a pressure surface includes a non-support-wall side linear portion formed to have a linear shape.

Abstract: A wind turbine blade (10) is described having a serrated trailing edge (20). Splitter plates (106) are provided on the blade, to reduce operational noise. Each splitter plate (106) is arranged to extend at least partly into a space in between adjacent serrations. The splitter plates can be formed integrally with the serrations, or attached to existing serrations as a retrofit solution. The serrations with the splitter plates can be provided as a trailing edge panel (108) for attachment to the trailing edge of an existing wind turbine blade.

Abstract: An impeller locking device for a wind generator is provided. The impeller locking device includes a locking hole formed on an impeller connecting disc, and a locking pin configured to fit into the locking hole. The locking pin is connected with a base of the wind generator; and when the locking pin is locked in the locking hole, a radial clearance is provided between the locking pin and the locking hole. When the axes of the locking pins and the locking holes are deviated radially, the locking pins can also be inserted into the locking holes, so that radial constraints of the locking pins and the locking holes are eliminated. A wind generator adopting the impeller locking device is further provided.

Abstract: A rotor hub is presented that uses a low profile and frontal area design that reduces drag and combines the advantages of utilizing a virtual flapping hinge and a soft in-plane rotor hub.

Abstract: An airfoil and shroud assembly includes an airfoil including a root end, a free end and a tenon extending from the free end, the tenon including a base and an externally threaded stud extending from the base. A shroud includes an opening configured to receive the base of the tenon. A nut is configured to be threadably coupled to the externally threaded stud on the tenon on the airfoil to couple the shroud to the airfoil.

Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.

Abstract: The present disclosure provides an oil pump including a housing in which a space is formed, a rotor installed to be rotatable in an eccentric position in the housing and having vanes mounted along a circumference direction to be protruded and retracted in a radial direction of the housing, and an inner ring fitted to an inner surface of the housing and rotated along with the rotor when the rotor rotates. The housing is formed of a material harder than the material of the inner ring, and oil for lubrication is provided between the housing and the inner ring.

Abstract: A turbulent air reducer assembly for a gas turbine engine includes a windage cover attached to a first standoff and a second standoff, the windage cover tuned to a particular vibration response. A method of managing air within a turbine of a gas turbine engine includes reducing turbulence from a multiple of recesses within a tangential on-board injector with a turbulent air reducer assembly within each of the multiple of recesses, the turbulent air reducer assembly tuned to a particular vibration response from a turbine rotor.

Abstract: An axial fan includes an upper impeller disposed in an axially upper portion of a housing, and an upper circuit board disposed axially below the upper impeller. An upper impeller cup of the upper impeller includes an upper cylindrical portion and an upper lid. The axial fan includes a lower impeller disposed in an axially lower portion of the housing, and a lower circuit board disposed axially above the lower impeller. A lower impeller cup of the lower impeller includes a lower cylindrical portion and a lower lid. An axial upper end outer diameter of the upper cylindrical portion is smaller than an axial lower end outer diameter of the upper cylindrical portion. An axial lower end outer diameter of the lower cylindrical portion is smaller than an axial upper end outer diameter of the lower cylindrical portion.

Abstract: A blade body made of composite material includes fiber reinforcement densified by a matrix, the blade body extending in a longitudinal direction between a root or bottom portion and a tip or top portion, and in a transverse direction between a leading edge and a trailing edge. The fiber reinforcement of the blade body includes a first portion constituted by a plurality of yarn layers interlinked by three-dimensional or multilayer weaving, and a second portion forming all or part of at least one leading edge or at least one trailing edge of a blade. The second portion includes a plurality of short fibers oriented in random manner, the yarns of the plurality of yarn layers of the first portion and the short fibers of the second portion being embedded in the matrix.

Abstract: A bowed-rotor prevention system for a turbomachine is disclosed. The system comprises a first turbomachine having a first shaft rotatably supported by a plurality of bearings, a second turbomachine having a second shaft rotatably coupled to the first rotatable shaft, and a pump having a third shaft rotatably coupled to the second shaft. The system further includes a gear box having a fourth shaft rotatably coupled to the third shaft by an clutch configured to operate in a freewheel condition when the first shaft is rotating faster than a first predetermined speed, and further configured to rotatably engage the fourth shaft to the third shaft when the first shaft is rotating slower than a second predetermined speed to thereby drive a rotation of the third shaft, wherein the first predetermined speed is faster than the second predetermined speed.

Abstract: A method of controlling a wind turbine is described. The method comprises calculating a current wear rate for each of the main bearing of a turbine rotor and the blade bearings of rotor blades mounted on the turbine rotor, and calculating a blade pitch adjustment of the rotor blades to achieved a desired ratio between main bearing wear and blade bearing wear in dependence on the calculated current wear rates of the main bearing and the blade bearings.

Abstract: A segmented flow path assembly and spline seals therefore are provided. A method for cooling a spline seal is also provided. In one exemplary aspect, a spline seal is provided that may be positioned at least in part in a groove defined by a first flowpath segment and at least in part in a oppositely facing groove defined by an adjacent flowpath segment. The spline seal may span the gap between the adjacent flowpath segments and provide sealing therefore. The spline seal includes features that allow a cooling flow to bypass the spline seal to cool the hot side of the seal as well as to meter the flow by the seal.

Abstract: Ceramic matrix composite (CMC) airfoils and methods for forming CMC airfoils are provided. In one embodiment, an airfoil is provided that includes opposite pressure and suction sides extending radially along a span and opposite leading and trailing edges extending radially along the span. The leading edge defines a forward end of the airfoil, and the trailing edge defines an aft end of the airfoil. A trailing edge portion is defined adjacent the trailing edge at the aft end, and a pocket is defined in and extends within the trailing edge portion. A heat pipe is received in the pocket. A method for forming an airfoil is provided that includes laying up a CMC material to form an airfoil preform assembly; processing the airfoil preform assembly; defining a pocket in a trailing edge portion of the airfoil; and inserting a heat pipe into the pocket.